STAR-C -CCM+ CM+ Applied ied to AIAA HiLif LiftW tWS1 S1 D. - - PowerPoint PPT Presentation

High gh-Lif Lift t Aerodyn dynamics amics: : STAR-C

• CCM+

CM+ Applied ied to AIAA HiLif LiftW tWS1 S1

• D. Snyder

er

Aerodyna nami mics cs

– Subsonic through Hypersonic – Aeroacoustics – Store release & weapons bay analysis – High lift devices – Stage separation – Plume analysis – Ablation – Engine integration

Aer erospa space ce App pplic icati tion

• n Area

eas

Aerodyna nami mics cs

– Subsonic through Hypersonic – Aeroacoustics – Store release & weapons bay analysis – High lift devices – Stage separation – Plume analysis – Ablation – Engine integration

Propulsi sion

• n Systems

ems

– Pumps – Rocket Motor, Ramjet, & Scramjet – Fans and Turbines – Combustion, sprays, chemistry – Inlets & ducting – Nozzles – Fuel systems, sloshing – Filters

Aer erospa space ce App pplic icati tion

• n Area

eas

Aerodyna nami mics cs

– Subsonic through Hypersonic – Aeroacoustics – Store release & weapons bay analysis – High lift devices – Stage separation – Plume analysis – Ablation – Engine integration

Propulsi sion

• n Systems

ems

– Pumps – Rocket Motor, Ramjet & Scramjet – Fans and Turbines – Combustion, sprays, chemistry – Inlets & ducting – Nozzles – Fuel systems, sloshing – Filters

Heat Transfer er and Thermal al Manageme agement nt

– Mechanical Systems (APU’s, undercowling, etc.) – Ice Protection – Avionics / Electronics Systems – Battery Heat Management – Heat Exchangers – Blade cooling – Other Conjugate Heat Transfer

Aer erospa space ce App pplic icati tion

• n Area

eas

Aerod

• dynamics

ynamics of 3D swep ept t wings gs in high-lif ift t conf nfigu gurat ations ions is very y compl plex

– Separation – Unsteadiness – Confluent boundary layers – Transition – Vortical flow

AI AIAA AA HiLif iftW tWS1 S1 (2010) 0)

– Assess capabilities of current-generation codes

• Meshing
• Numerics
• Turbulence Modeling
• High-performance computing

High gh-Lif Lift t Aerodyn dynamics amics

Tested ed in 1998 98-1999, 99, 2002 02-2003 2003 at NAS ASA Lang ngle ley y and NAS ASA Am Ames es wind nd tun unne nels Re ~ 4.6M 6M

– No turbulent trips – transition is a factor

Data collect lected ed

– Aerodynamic forces/moments* – Pressure distributions* – Transition location – Acoustics

NASA ‘Trap Wing’ Model

*Evaluated in HiLiftWS1

Trap Wing in NASA LaRC 14x22 WT

Geome

• metr

try y provided vided in IGES ES forma rmat

– Minor surface cleanup

“Configuration 1”

– Slats at 30 deg, Flaps at 25 deg – Fully-deployed configuration

Farfiel ield boundar ndaries ies created d in STAR AR-CCM CM+

– Extend 100MAC in all directions

Computation putational al Domain ain

No No-slip lip wall conditions nditions

– No transition location specified

Symm mmetr try y plane ne Frees eestr tream eam

– Mach 0.2 – T = 520R – P = 1 ATM – (Re = 4.3M based on MAC) – a = 6, 13, 21, 28, 32, 34, 35, 36, 37 deg

Boundar dary y Condit ditions ions

Polyhe yhedral dral mesh sh

– Wide range of angles of attack on a single mesh – Strong streamline curvature – Massive recirculation regions

Prism m layer ers

– 30 layers

Grid refinem inement nt study udy

– Results from Medium grid are presented

Mesh Overvie iew

Grid Size Number of cells Very Coarse 10M Coarse 21M Medium 34M Fine 43M

*Very Coarse mesh shown (10M cells)

Text

Addit ition ional al Mesh h Features tures

*Very Coarse mesh shown (10M cells)

Densi nsity ty-Ba Base sed d Coupled upled Solver er

– Low Mach number preconditioning

2nd-order der sp spatial al disc scre retizati tization

• n

Stea eady dy-st stat ate e RAN ANS S equa uation ions SST T (Ment nter) ) k-w Tur urbulence ulence Mode del

– Integrated to the wall – 1st prism layer y+ < 1.0 – g-Reθ Transition Model

Solver er Sett ettings gs

g-Re Reθ Trans nsiti ition

• n Model

– Predicts laminar-turbulent transition in the boundary layer – Correlation-based model formulated for unstructured CFD codes – Models transport of Momentum Thickness Re and Intermittency

Without

• ut tran

ansiti ition

• n modeling

ing

– Lift coefficient generally underpredicted – Stall predicted too late

Transit ansition ion Model

Transition AoA=13°

Converge ergence ce Behavior ior

0.5 1 1.5 2 2.5 3 3.5 2000 4000 6000 8000 10000 12000 14000 CL Iterations (n) 6 degrees 13 degrees 21 degrees 28 degrees 32 degrees 34 degrees

Turn on transition model

*At higher angles of attack, stability required running without transition model for a time.

Comple plex x Flowfield ield

AOA=6 =6 AOA=13 AOA=3 =37 AOA=2 =28

Lift t Pred edicti iction

• n

0.5 1 1.5 2 2.5 3 3.5

• 5

5 10 15 20 25 30 35 40 CL Angle of Attack (Degrees)

Configuration 1

Experiment STAR-CCM+: Medium

Lift t Pred edicti iction

• n

0.5 1 1.5 2 2.5 3 3.5

• 5

5 10 15 20 25 30 35 40 CL Angle of Attack (Degrees)

Configuration 1

Experiment STAR-CCM+: Medium

Drag g Predic edictio tion

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

• 5

5 10 15 20 25 30 35 40 CD Angle of Attack (Degrees) Experiment STAR-CCM+: Medium

Pitch tching ing Momen ent t Predic edicti tion

• n
• 0.6
• 0.5
• 0.4
• 0.3
• 0.2
• 0.1
• 5

5 10 15 20 25 30 35 40 CM Angle of Attack (Degrees) Experiment STAR-CCM+: Medium

Pressur ssure e mea easure sureme ments nts were ere made de at ~800 00 locati tions

• ns on the

e wing g sur urface face Similar ilarly ly, CFD data was s extr tract cted ed at 9 corres rrespond ponding ng sp spanwis wise locati tions

• ns

Pressure essure Data

0.17 0.28 0.41 0.50 0.65 0.70 0.85 0.95 0.98

Experimental pressure tap locations CFD data extraction locations

Cp Cp Comparison: η=0.50 (mid-span) an)

AoA=6° AoA=21° AoA=34° AoA=37°

Cp Cp Comparison arison: η=0.95 (tip)

AoA=6° AoA=21° AoA=34° AoA=37°

STAR AR-CC CCM+ M+ accur urat ately ely predict dicted ed the e aerodynamic behavior of the NASA ‘Trap Wing’ high-lif lift t case se

– Lift, drag, and pitching moment – Pressure distribution

Proper per mesh shing ing techni chniques es were re imp mpor

• rta

tant nt

– Boundary layer – Element wake interactions – Massive separation region – Tip vortex

Trans nsit ition ion mode deling ing was necess cessar ary

– Fully-turbulent under-predicted lift at high AoA (pre-stall) – Fully-turbulent over-predicted stall AoA

Conclusions lusions

AoA=6° AoA=21°

HiLif iftW tWS1 S1 Speci cial al Sessi sion

• n

(Jun une e 2012) 12)

– Addition of support brackets – Hysteresis effects

Aeroe

• elas

astic tic Predic dicti tion

• n Worksh

kshop

• p (Ap

April l 2012) 12) Propulsi ulsion

• n Aerodyn
• dynamic

amics s Worksh kshop

• p

(Jul uly y 2012) 12) Eg Eglin Store re Separa rati tion

• n Valida

dati tion

• n

Up Upcomi ming

Quest stions? ions?